chandrayaan mission objectives and future lunar programs · 10/2/2007 · lunar transfer...

Chandrayaan Mission Objectives and future lunar programs

CHANDRAYAAN - I

Paul Spudis, channeling J. N. GoswamiPrincipal Scientist, Chandrayaan-1 Mission

III. The bulk chemistry of Moon, particularly the abundance of iron, magnesium and uranium

II. Melting of the Moon: The Magma Ocean Hypothesis

IV. Lunar asymmetries & formation of SPA basin

V. The nature and structure of the lunar crust and mantle

VI. Water on Moon and the nature of Volatile transport

I. Origin of the Moon: Chance or Destiny?

The Clementine & Lunar Prospector Missions to Moon raised

New Questions about the Evolution of Moon

And, the List is growing……..

Understanding the origin and Evolution of the Moon

The lunar far side: rock types, chemistry

Nature of the Lunar Crust

Physical Properties of the Moon

Topography

Gravity

Magnetic FieldRadiation Environment

Nature of Volatile Transport on Moon (Water on Moon?)

Special Regions of Interest:

Polar Regions ,

South Pole-Aitken Basin Region,

Selected Basins and Craters as windows into the crust

Nature of the Magma Ocean and Lunar Interior

The bulk chemistry of Moon

Simultaneous Mineralogical, Chemical and Photogeological Mapping at resolutions better than previous and currently planned lunar missions

Direct estimation of lunar surface concentration of the elements Mg, Al, Si, Ca, Ti and Fe with high spatial resolution (20 km)

Volatile Transport to colder polar regions (using Pb-210 as tracer)

Objectives of the Chandrayaan-1 Mission

3D mapping of lunar surface at very high spatial resolution (~5 m)

High resolution UV-VIS-NIR mapping of the lunar surface to identify mineralogy and selected elements (Fe, Al, Mg, Ti)

Configuration : 100 km polar orbiter

Observation Period : 2 years

Terrain Mapping Camera (TMC)

Laser Ranging (LLRI)

High energy X-γ

ray spectrometer (HEX) (10-200KeV)

Moon Impact Probe (MIP), camera and altimeter hard lander

Chandrayaan-1 Mission

Hyper Spectral Imager (HySI) (0.4-0.9µm)

Baseline Payloads:

Imaging Payloads on Chandrayaan-1

I. Terrain Mapping Camera (TMC)

Stereoscopic instrument in Panchromatic band for3D Topographic mapping with high spatial

and altitude resolution.

II. Hyper Spectral Imager (HySI)

Imager for Mineralogical mapping in UV-VIS-NIR with high spectral resolution.


[Designed and Fabricated at the Space Application Center, ISRO]

Fore Viewing

Nadir Viewing

Aft Viewing

TMC concept & Instrument configuration


1060 nm LASER BEAM

BEAM EXPANDER

Nd YAG LASER

POWER SUPPLY & THERMAL INERFACE

ATTITUDE & POSITION

RANGE RECEIVER & DATA ACQUISITION

Lunar Laser Ranging Instrument

Primary Objective:Determine Global Topographic Figure of Moon

●●

Supplement TMC and HySI Imager●

Improved model of lunar gravity fieldDeveloped at LEOS, ISRO


HySI concept & Instrument configuration

X1Xn

X1 Xn

Spectral Dimension (λ)

Objective

Detection Array Area

Wedge Filter

Flight Direction

400-900 nm, 32 bands, resolution 80 m


Compact Imaging X-ray Spectrometer (CIXS)

Chemical (Elemental) Mapping of Lunar Surface based on

Solar X-ray induced fluorescence emission

[Mg, Al, Si : Solar quiet time]

Ca, Ti, Fe : Solar Flare time]

High resolution mapping of Fe and estimation of Mg#

A modified version of D-CIXS, the Low Energy X-ray Spectrometer, flown on SMART-1

P. I. Prof. Manuel Grande, Rutherford Appleton Laboratory, UK Indian Co-I : Dr. P. Sreekumar, ISAC

New generation Swept-charge X-ray Detector


●●

Volatile Transport on Moon through detection of 46.5 keV line from Pb-210

●●

Th and U map of Polar and U-Th-rich regions

High Energy X- γ

Ray (HEX) PAYLOAD

Basic Features

Detector: Cd-Zn-Te Array

Effective Area: 100 cm2

Energy Range: 20-250 keV

Energy Resolution: ≤6% @ 60 keV

FOV: 40km x 40km

Active Anticoincidence Shielding: CsI(Tl)+PMT

Collimator: Tantalum

Weight: 15 kg

Power: 23 WDeveloped by Physical Research Laboratory & ISRO Satellite Center


High Energy X- γ

Ray Spectrometer (10-200 KeV)

CdZnTe Array Detector with Collimator

High Energy X- γ

Ray (HEX)

First attempt to detect low-energy (20-250 keV) gamma ray emission from a planetary surface

Mapping of U, Th and Pb-210

α

206Pb

~ - 1700C

SUN

226Ra 1622yα

222Rn (γ)

3.8d (gas)α

218Po 3.05mα

214Pb 23.8m

214Bi 19.7m

214Po 1.6x10-4sα

210Pb (γ) 22.3y paint

210Bi 5.01d210Po 138d

~ +120 0C

Water on Moon: Movement of volatile (222Rn) to permanently shadowed polar regions using 210Pb (46 keV) as tracer

Source: U-238 in Moon

Payload Configuration & DetailsPayload Configuration Range Resolution Objective

Hyper Spectral Imager (HySI)

Wedge filter pixelated imager

0.4-0.9 μm

Spatial - 80mSpectral-15nm32 channels

Mineralogical mapping

Terrain Mapping Camera (TMC)

Three stereo cameras with pixelated imagers

Panchrom -atic; 20 km swath

Spatial - 5mVertical - 5m

High resolution Atlas of the whole moon

Laser ranging(LLRI)

Pulsed Nd-Yag laser 1064 nm

Vertical -10 m or better

Topography & Gravity model

Compact X-ray Spectrometer(CIXS)

X-ray SCXD type detector 25 sq. cm area

0.5-10 keV

20 km Elemental mapping Si, Al, Mg, Ca, Fe, Ti

High energy X- ray spectrometer(HEX)

CdZnTe detector 100 sq. cm. area

10-200 keV

40 km 210Pb, Volatile transport

Solar X-ray Monitor (SXM)

Si-Pin Diode2 or 3 detectors viewing orthogonally

2-10 keV Solar X-ray flux monitoring


A new era of International Cooperation

Based on science objectives and spacecraft resources, several proposals were accepted from international community; they complement/add to the Indian experiments to meet the basic

science goals of the mission.

I. IR spectrometers for mineral mapping (SIR-2 and MMM)

II. An experiment to detect neutral atoms (SARA)

III. An experiment to map the poles and search for water ice (mini-SAR)

IV. An experiment to monitor energetic particle environment (RADOM)

There will be Indian collaboration in analyzing data from all these experiments


Chandrayaan-1 Mission (AO Payloads)

SIR-2: A Near-infrared SpectrometerP. I. Dr. Urs Mall,

Max-Planck Institute for Solar System Research Katlenburg-Lindau, Germany

The first version of SIR orbited the Moon onboard ESA SMART-1 Mission

Spot spectrometer 1.11 milliradian FOV (~110 m surface spot size from 100 km orbit)

930-2400 nm spectral range with 6 nm spectral resolution


Mineral Mapping of Lunar Surface

Moon Mineralogy MapperAn Imager in VIS-NIR band

P. I. Dr. C. Pieters, Brown University , USA

This Instrument, together with SIR-2, HySI, CIXS and SARA, provide detailed mapping of surface composition of the Moon

700 to 3000 nm rangeSampling : 10 nanometersSpatial resolution: 70 m/pixel [from 100 km orbit]Field of View: 40 km [from 100 km orbit]Weight: ~7 kgPower average: ~13 W

SARA: Sub-KeV Atom Reflecting AnalyzerP. I. Dr Stas Barabash,Swedish Institute of Space Physics &

Dr. A. Bharadwaj, Space Physics Laboratory, India

Basic Science Objective : Imaging of: (i) Moon’s surface composition (ii) lunar surface magnetic anomalies

Anticipated Highlights:

Surface composition of permanently shadowed areas and complement data from other payloads on surface composition

Surface magnetic anomalies: magnitudes and plausible causes


SENA SWIM

RADOM: Radiation characterizationBulgarian Academy of Sciences

Basic Science Objective : Characterization of lunar radiation environment and efficacy of shielding effects by lunar materials

Anticipated Highlights:Particle flux, deposited energy spectrum, accumulated absorbed dose rates in Lunar orbit

Estimate dose around Moon at different altitudes and latitudes

Evaluate the shielding characteristics (if any) of the near-Moon environment towards galactic and solar cosmic radiation and solar particle events


Mini-SAR: A Miniature Synthetic Aperture Radar

P. I. Dr. Paul D. Spudis: Applied Physics Laboratory, Johns Hopkins University

Basic Science Objective: Map terrain of lunar poles and determine surface scattering properties of deposits to search for ice in the permanently shadowed regions of the poles

Uses unique hybrid architecture to reconstruct Stokes matrix scattering parameters

Prospector Mission

Radar reflections mimicking volume-scattering behavior of ICE

Neutron Spectrometer suggests presence of excess hydrogen (water?) in polar regions

Clementine Mission


Salient features of Chandrayaan-1 Mission

Elemental mapping of the moon (Mg, Al, Si, Ca, Ti and Fe) using both X-ray Fluorescence and UV-VIS-IR spectroscopy;

First set of detail data for Fe (from XRF) and mineralogy (IR region)

Timing of the mission: Mid-level to high level of solar flare activity

Prospector data for Fe from gamma-ray observation suffers from low spatial resolution (150 km) and Al interference

The Mg* [Mg/(Mg+Fe)] is one of the MOST IMPORTANT diagnostic parameters to understand lunar bulk composition

LEX, HySI, SIR-2, MMM (also SARA; shaded area)

High resolution Global Chemical Mapping


First attempt to detect emission of low energy (

SIR-2

HySI

CIXS

MINI-SAR

SWIM

LLRI

HEX

IMPACT PROBERADOM

LENA

PAY LOAD ACCOMMODATION

TMC

MMM


Sun

Moon at Launch

ETOGTO

Lunar Transfer Trajectory

Lunar Insertion Manoeuvre

Mid Course Correction

Trans Lunar Injection

Initial Orbit ~ 1000 km

Final Orbit 100 km Polar

To achieve 100 x 100 km Lunar Polar Orbit.PSLV to inject 1050 kg in GTO of 240 x 36000 km.

Lunar Orbital mass of 523 kg with 2 year life time.

Scientific payload 62 kg.


Launch Of Chandrayaan – I by PSLV

(Target Date: April, 2008 )

Altitude = 100km;

Inclination = 90o

Period = 117.6 min.

Track Repeat = 28 days


A National Science Data Center will be established to host data from Chandrayaan-1 and other Science Missions (e.g., ASTROSAT-1);

Instrument Specific Software Packages for generation of Data Products and Analysis will be available at the Data Center

Spacecraft and Instrument data will be available to PI and Team on real time

Final Data Products and format for archiving have been formulated

Data sharing between various PI groups for enhancing Science return

Instrument Calibration: Laboratory Calibration to cover ALL aspects. Additional Calibration during Tran lunar cruise as well as in lunar orbit, if needed

Chandrayaan 2

•

Proposed launch 2010-2011•

Orbital spacecraft and surface rover

•

Rover 30-100 kg; semi-hard or soft landing•

Solar powered; may be designed to hibernate during lunar night for a second two weeks of operation

•

Instruments TBD, but will conduct compositional analysis of surface materials

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chandrayaan mission objectives and future lunar programs · 10/2/2007 · lunar transfer...

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